Advanced engine cycles are being developed to improve aircraft performance. One cycle getting attention is the multi-stream engine. This type of engine has an additional stream that needs to be introduced into the core stream. Introduction of the additional stream occurs downstream of nozzle throat. Care must be taken to ensure the method of introduction does not destroy any benefits of the additional stream. In this work, two splitter plate geometries used to separate the streams are studied using Large-Eddy Simulation (LES) via the Naval Research Laboratory's (NRL's) JENRE code. The trailing edge of the splitter plates are a flat edge and a knife edge. The flat edge is known to create a persistent tone in both the near and far fields and mixes the two stream faster than desired while the knife edge eliminates this tone, reduces the mixing, and provides shielding from shocks.
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